Numerical simulations of compressible flows over airfoils.
A computer code was developed from scratch to simulate the flow over the NACA 0012 airfoil at different Reynolds and Mach numbers. The domain was discretized in a structured-grid context. The equations were numerically solved by a finite-volume technique, using three different time-marching schemes....
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| Format: | Others |
| Language: | English |
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Instituto Tecnológico de Aeronáutica
2006
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| Online Access: | http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=316 |